JP2002003747A - Coating material and heat-resistant member using the same - Google Patents
Coating material and heat-resistant member using the sameInfo
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- JP2002003747A JP2002003747A JP2000184789A JP2000184789A JP2002003747A JP 2002003747 A JP2002003747 A JP 2002003747A JP 2000184789 A JP2000184789 A JP 2000184789A JP 2000184789 A JP2000184789 A JP 2000184789A JP 2002003747 A JP2002003747 A JP 2002003747A
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- Prior art keywords
- heat
- coating material
- weight
- resistant
- layer
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Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、高温耐久性、特に
高温における耐剥離性に優れたコーティング材及びそれ
を用いた耐熱部材（特にガスタービン用翼）に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a coating material having excellent high-temperature durability, especially high-temperature peeling resistance, and a heat-resistant member using the same (especially a gas turbine blade).
【０００２】[0002]
【従来の技術】高い耐熱性が要求される部材では、例え
ば、発電用ガスタービンなどの部材（高温又は耐熱部
材）は、一般に耐熱鋼や耐熱合金などの耐熱材料で形成
されている。特に、入口温度の高いガスタービンなどで
は、耐熱部材（第一段動静翼など）の使用温度が、部材
を形成する耐熱材料の耐用温度を超える場合も多い。そ
のため、耐熱部材は、通常、さらに皮膜により保護（コ
ーティング）されている。2. Description of the Related Art In a member requiring high heat resistance, a member such as a gas turbine for power generation (a high-temperature or heat-resistant member) is generally formed of a heat-resistant material such as a heat-resistant steel or a heat-resistant alloy. In particular, in a gas turbine or the like having a high inlet temperature, the use temperature of the heat-resistant member (such as the first-stage moving vane) often exceeds the service temperature of the heat-resistant material forming the member. Therefore, the heat-resistant member is usually further protected (coated) by a film.
【０００３】このようなコーティング材としては、基材
に比べて、クロムやアルミニウムなどの耐熱性や耐酸化
性が高い成分を多く含有するコーティング材、ＭＣｒＡ
ｌＹで表される金属（合金）で構成されたコーティング
材、ＺｒＯ2などのセラミックスで構成されたコーティ
ング材や、前記ＭＣｒＡｌＹで構成された中間層（ボン
ドコート）と前記セラミックスで構成された表面遮断層
（トップコート）とを組み合わせた複合コーティング材
などが使用されている。[0003] As such a coating material, a coating material containing a large amount of components having high heat resistance and oxidation resistance, such as chromium and aluminum, compared with the base material, MCrA
a coating material composed of a metal (alloy) represented by 1Y, a coating material composed of ceramics such as ZrO 2, or an intermediate layer (bond coat) composed of MCrAlY and a surface barrier composed of the ceramics A composite coating material combining a layer (top coat) and the like are used.
【０００４】近年、発電効率の向上を目的として、蒸気
投入型ガスタービンなどの導入も増加し、ガスタービン
における燃焼ガス温度がさらに高温化するにつれて、ガ
スタービン用の耐熱部材の使用環境も過酷化する傾向に
あり、コーティング材の果たす役割は重要度を増してい
る。このような使用環境では、高温、水蒸気雰囲気、基
材とコーティング材との熱膨張差に起因する熱応力や、
タービンのオン／オフにより発生する熱応力などの種々
の要因により、コーティング材の劣化が進行するため、
前記のような従来のコーティング材では、実用上十分な
耐久性が得られない場合も多く、高度な耐熱性能が要求
されている。また、ガスタービン用の高温部材は、非常
に高価であるため、コーティング材の寿命を延長化でき
れば、大幅なコストダウンが可能である。[0004] In recent years, the introduction of steam-input gas turbines and the like for the purpose of improving power generation efficiency has increased, and as the combustion gas temperature in gas turbines has further increased, the use environment of heat-resistant members for gas turbines has become severer. And the role played by the coating material is increasing in importance. In such use environment, high temperature, steam atmosphere, thermal stress due to the difference in thermal expansion between the substrate and the coating material,
Due to various factors such as thermal stress generated by turning on / off the turbine, deterioration of the coating material progresses.
In the conventional coating materials as described above, in many cases, practically sufficient durability cannot be obtained, and high heat resistance is required. Further, since a high-temperature member for a gas turbine is very expensive, if the life of the coating material can be extended, a significant cost reduction can be achieved.
【０００５】このような観点から、コーティング材の耐
久性向上を目的として、基材との密着性を向上させるこ
とにより、耐熱性及び耐久性を改善する方法などが検討
されている。例えば、特開平８−８５８８３号公報に
は、耐熱合金基材の表面に、基材に比べ高温耐食耐酸化
性に優れた合金からなるメタル層とＺｒＯ2系セラミッ
クス層とが形成され、前記メタル層とＺｒＯ2セラミッ
クス層との中間に、前記メタル層の成分及びセラミック
ス層の成分を含む酸化物からなる結合層を有する耐熱部
材が開示されている。[0005] From such a viewpoint, for the purpose of improving the durability of the coating material, a method of improving the heat resistance and the durability by improving the adhesiveness to the substrate has been studied. For example, JP-A-8-85883 discloses that a metal layer made of an alloy having better high-temperature corrosion resistance and oxidation resistance than a substrate and a ZrO 2 -based ceramic layer are formed on the surface of a heat-resistant alloy substrate. A heat-resistant member having a bonding layer made of an oxide containing the components of the metal layer and the components of the ceramic layer between the layer and the ZrO 2 ceramic layer is disclosed.
【０００６】また、NASAテクニカルメモ（Optimization
of the NiCrAl-Y／ZrO3-Y2O3 Thermal Barrier System
s 1985)に記載されているように、ＭＣｒＡｌＹの成分
割合とその剥離寿命との間には密接な関係があることが
知られている。そのため、成分割合を変化させることに
より、耐熱性を向上する方法が検討されている。このよ
うな方法としては、例えば、特開平５−７８８６０号公
報には、耐熱合金製基材の表面に、Ｃｏを主成分とする
ＭＣｒＡｌＹ層（下部合金被覆層）と、Ｎｉを主成分と
するＭＣｒＡｌＹ層（上部合金被覆層）とを設けた合金
ガスタービン翼が開示されており、前記上部合金被覆層
のＡｌ含有量を最外表面部で大きく内側で連続的に減少
させている。Further, a NASA technical memo (Optimization
of the NiCrAl-Y / ZrO3-Y2O3 Thermal Barrier System
s 1985), it is known that there is a close relationship between the component ratio of MCrAlY and its stripping life. Therefore, a method for improving heat resistance by changing the component ratio has been studied. As such a method, for example, Japanese Patent Application Laid-Open No. Hei 5-78860 discloses that an MCrAlY layer (lower alloy coating layer) containing Co as a main component and Ni as a main component are formed on the surface of a heat-resistant alloy substrate. An alloy gas turbine blade provided with an MCrAlY layer (upper alloy coating layer) is disclosed, in which the Al content of the upper alloy coating layer is greatly reduced at the outermost surface and continuously reduced inside.
【０００７】しかし、上記のいずれの方法でも、実用上
十分な耐熱性及び耐久性を得るためには、コーティング
の多層化が避けられず、製造工程が非常に煩雑になるた
め、経済的にも不利である。However, in order to obtain practically sufficient heat resistance and durability in any of the above methods, it is inevitable that the coating is multi-layered, and the production process becomes very complicated. Disadvantageous.
【０００８】[0008]
【発明が解決しようとする課題】従って、本発明の目的
は、低コストでありながら、優れた耐熱性及び耐久性を
有するコーティング材、及びそれを用いた耐熱部材を提
供することにある。SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide a coating material having excellent heat resistance and durability at low cost, and a heat-resistant member using the same.
【０００９】本発明の他の目的は、前記コーティング材
で構成された耐熱層上に、さらに表面層を形成するため
のコーティング材を提供することにある。Another object of the present invention is to provide a coating material for forming a surface layer on the heat-resistant layer composed of the coating material.
【００１０】[0010]
【課題を解決するための手段】本発明者らは、前記課題
を達成するため鋭意検討した結果、特定の成分組成を有
するＣｏ／Ｎｉ系の合金でコーティング材を構成する
と、工程を増加させることなく、耐熱性及び耐久性を容
易に改善できることを見出し、本発明を完成した。Means for Solving the Problems The inventors of the present invention have conducted intensive studies to achieve the above object, and as a result, it has been found that if a coating material is made of a Co / Ni-based alloy having a specific component composition, the number of steps can be increased. And found that the heat resistance and durability can be easily improved, and completed the present invention.
【００１１】すなわち、本発明のコーティング材（第１
のコーティング材）は、耐熱合金製基材をコーティング
するためのコーティング材であって、下記式 ＭＣｒＡｌＹ （式中、ＭはＮｉ及びＣｏを示す）で表される成分と不
可避的不純物とで構成され、Ｃｒ含量が２１〜２８重量
％、Ａｌ含量が４〜７．５重量％、及びＹ含量が０．０
５〜１．２重量％である。ニッケル及びコバルトの総量
１００重量部に対するＡｌの割合は、６〜１０重量部程
度であってもよい。That is, the coating material of the present invention (first
Is a coating material for coating a substrate made of a heat-resistant alloy, and is composed of a component represented by the following formula MCrAlY (where M represents Ni and Co) and unavoidable impurities. , A Cr content of 21 to 28% by weight, an Al content of 4 to 7.5% by weight, and a Y content of 0.0
5 to 1.2% by weight. The ratio of Al to 100 parts by weight of the total amount of nickel and cobalt may be about 6 to 10 parts by weight.
【００１２】本発明には、前記コーティング材で構成さ
れた耐熱層をコーティングするためのコーティング材
（第２のコーティング材）であって、Ｙ2Ｏ3、ＭｇＯ、
ＣｅＯ 2、ＣａＯなどの安定剤で安定化されたＺｒＯ2系
セラミックスで構成されているコーティング材も含まれ
る。According to the present invention, there is provided the above-mentioned coating material.
Coating material for coating heat resistant layers
(Second coating material), and YTwoOThree, MgO,
CeO TwoStabilized with a stabilizer such as CaO and CaOTwosystem
Also includes coating materials composed of ceramics
You.
【００１３】本発明には、さらに、耐熱合金製基材の表
面に、前記耐熱コーティング材で構成された耐熱層が形
成されている耐熱部材（ガスタービン翼など）も含まれ
る。The present invention further includes a heat-resistant member (such as a gas turbine blade) in which a heat-resistant layer made of the heat-resistant coating material is formed on the surface of a heat-resistant alloy base material.
【００１４】[0014]
【発明の実施の形態】［コーティング材］本発明のコー
ティング材（第１のコーティング材）は、Ｎｉ／Ｃｏ系
合金、すなわち、Ｎｉ及びＣｏをベース金属成分とし、
下記式で表される成分と不可避的成分（不可避的不純
物）とで構成されている。BEST MODE FOR CARRYING OUT THE INVENTION [Coating Material] The coating material (first coating material) of the present invention is a Ni / Co alloy, that is, Ni and Co as base metal components,
It is composed of a component represented by the following formula and an unavoidable component (unavoidable impurity).
【００１５】ＭＣｒＡｌＹ （式中、ＭはＮｉ及びＣｏを示す）前記Ｎｉ／Ｃｏ系合
金において、Ｃｒ、Ａｌ及びＹ含量が、特定の範囲であ
る場合に、経済性と耐久性とを両立できる。このような
Ｃｒ含量は、Ｎｉ／Ｃｏ系合金全体に対して、２１〜２
８重量％、好ましくは２３〜２６重量％（例えば２４〜
２６重量％）程度である。また、Ｎｉ／Ｃｏ系合金に対
して、Ａｌの含量は、４〜７．５重量％、好ましくは５
〜６．５重量％（例えば５．５〜６．５重量％）程度で
あり、Ｙ含量は、０．０５〜１．２重量％、好ましくは
０．８〜１．２重量％（例えば１〜１．２重量％）程度
である。MCrAlY (wherein M represents Ni and Co) In the above-mentioned Ni / Co alloy, when the Cr, Al and Y contents are in a specific range, both economy and durability can be achieved. Such a Cr content is 21 to 2 with respect to the entire Ni / Co alloy.
8% by weight, preferably 23 to 26% by weight (e.g.
26% by weight). Further, the content of Al is 4 to 7.5% by weight, preferably 5% by weight, based on the Ni / Co alloy.
To 6.5% by weight (e.g., 5.5 to 6.5% by weight), and the Y content is 0.05 to 1.2% by weight, preferably 0.8 to 1.2% by weight (e.g., 1%). １．２1.2% by weight).
【００１６】合金ＭＣｒＡｌＹ中のＣｒやＡｌは、安定
皮膜を形成し、基材に酸素が拡散するのを防止して、耐
酸化性を改善するようである。第１のコーティング材
（耐熱コーティング材）とＺｒＯ2系セラミックスで構
成された第２のコーティング材（遮熱コーティング材）
とを組み合わせて使用する場合（すなわち、第１のコー
ティング材層（耐熱層）を中間層とし、第２のコーティ
ング材層を表面層として使用する場合）には、Ａｌは耐
熱層と表面層との界面に、Ａｌ2Ｏ3が発生し、両層間の
密着性を低下させるようである。また、Ｙは、耐熱層上
に表面層を形成する場合、ＺｒＯ2と関連して耐熱層と
表面層との密着性の向上に寄与するようである。Cr and Al in the alloy MCrAlY appear to form a stable film, prevent oxygen from diffusing into the substrate, and improve oxidation resistance. First coating material (heat-resistant coating material) and second coating material (thermal barrier coating material) composed of ZrO 2 ceramics
(That is, when the first coating material layer (heat-resistant layer) is used as the intermediate layer and the second coating material layer is used as the surface layer), Al is used as the heat-resistant layer and the surface layer. It appears that Al 2 O 3 is generated at the interface of, and the adhesion between the two layers is reduced. Also, when forming a surface layer on the heat-resistant layer, Y seems to contribute to the improvement of the adhesion between the heat-resistant layer and the surface layer in relation to ZrO 2 .
【００１７】本願発明では、ＮｉとＣｏとを併用してベ
ース金属として使用することにより、Ａｌ含量を低含量
に抑えることができるため、剥離性を向上できるととも
に、耐熱性も維持できる。このようなＡｌ含量は、ニッ
ケル及びコバルトの総量１００重量部に対して、６〜１
０重量部、好ましくは７〜１０重量部（７〜９．５重量
部）、さらに好ましくは８〜９．５重量部程度である。In the present invention, by using Ni and Co in combination as a base metal, the Al content can be suppressed to a low content, so that the releasability can be improved and the heat resistance can be maintained. Such an Al content is 6 to 1 with respect to 100 parts by weight of the total amount of nickel and cobalt.
0 parts by weight, preferably 7 to 10 parts by weight (7 to 9.5 parts by weight), more preferably about 8 to 9.5 parts by weight.
【００１８】Ｎｉ及びＣｏの総量（Ａ）とＣｒ、Ａｌ及
びＹの総量（Ｂ）との重量割合は、Ａ／Ｂ＝９０／１０
〜５５／４５、好ましくは８０／２０〜６０／４０、さ
らに好ましくは７５／２５〜６５／３５程度であり、前
記（Ｂ）成分中のＡｌの割合は、（Ｂ）成分全体に対し
て、５〜３０重量％（例えば、１０〜３０重量％）、好
ましくは１５〜２５重量％、特に１７〜２０重量％程度
である。The weight ratio of the total amount of Ni and Co (A) to the total amount of Cr, Al and Y (B) is A / B = 90/10
55/45, preferably 80/20 to 60/40, more preferably about 75/25 to 65/35, and the proportion of Al in the component (B) is It is about 5 to 30% by weight (for example, 10 to 30% by weight), preferably about 15 to 25% by weight, particularly about 17 to 20% by weight.
【００１９】第１のコーティング材は、通常、鉄などの
金属元素の他、炭素、ケイ素、窒素、リン、酸素、硫黄
などの元素を含む不可避的不純物を含んでいる。The first coating material usually contains inevitable impurities including elements such as carbon, silicon, nitrogen, phosphorus, oxygen, and sulfur, in addition to metal elements such as iron.
【００２０】前記第１のコーティング材において、残余
は、Ｎｉ／Ｃｏ系合金のベース金属、すなわち、Ｎｉ及
びＣｏで構成される。Ｎｉ及びＣｏの総量は、Ｎｉ／Ｃ
ｏ系合金全体に対して、５０〜７０重量％、好ましくは
６０〜７０重量％、さらに好ましくは６５〜６９重量％
程度である。ＮｉとＣｏとの重量割合は、特に制限され
ないが、例えば、Ｎｉ／Ｃｏ＝１０／９０〜９０／１
０、好ましくは２０／８０〜７０／３０、さらに好まし
くは３０／７０〜５０／５０程度である。The remainder of the first coating material is composed of a base metal of a Ni / Co alloy, ie, Ni and Co. The total amount of Ni and Co is Ni / C
50 to 70% by weight, preferably 60 to 70% by weight, more preferably 65 to 69% by weight, based on the whole o-based alloy
It is about. Although the weight ratio of Ni and Co is not particularly limited, for example, Ni / Co = 10/90 to 90/1.
0, preferably about 20/80 to 70/30, and more preferably about 30/70 to 50/50.
【００２１】このような第１のコーティング材は、高度
な耐熱性能を有するため、耐熱合金製基材をコーティン
グし、耐熱用途での使用に適している。耐熱合金製基材
としては、慣用の耐熱合金製基材が使用できるが、耐熱
層との密着性を向上させるため、主成分であるＮｉやＣ
ｏを多く含有する合金製基材、例えば、Ｎｉ基鋳造合金
やＣｏ基鋳造合金などで構成された基材などを用いるの
が好ましい。Ｎｉ基鋳造合金、特に、Ｎｉ含量が５５重
量％以上（例えば５５〜８０重量％程度）のＮｉ基鋳造
合金は、ガスタービン用の動翼として好適に使用でき、
Ｃｏ基鋳造合金、特にＣｏ含量が４５重量％以上（例え
ば、４５〜９０重量％、好ましくは５０〜７０重量％程
度）のＣｏ基鋳造合金は、ガスタービン用の静翼として
好適に使用できる。本願発明のコーティング材は、上記
のような特定の成分含量において、特に前記Ｃｏ基鋳造
合金を基材として用いた場合に、耐剥離性の改善効果が
大きく、寿命を大幅に延長することができる。Since such a first coating material has a high heat-resistant performance, it is suitable for use in heat-resistant applications by coating a heat-resistant alloy base material. As the heat-resistant alloy substrate, a conventional heat-resistant alloy substrate can be used. However, in order to improve the adhesion with the heat-resistant layer, Ni or C, which is a main component, is used.
It is preferable to use an alloy base material containing a large amount of o, for example, a base material made of a Ni-based cast alloy, a Co-based cast alloy, or the like. A Ni-based casting alloy, particularly a Ni-based casting alloy having a Ni content of 55% by weight or more (for example, about 55 to 80% by weight) can be suitably used as a moving blade for a gas turbine.
Co-base cast alloys, particularly Co-base cast alloys having a Co content of 45% by weight or more (for example, about 45 to 90% by weight, preferably about 50 to 70% by weight) can be suitably used as stationary blades for gas turbines. The coating material of the present invention has the above-mentioned specific component content, particularly when the Co-based casting alloy is used as a base material, has a large effect of improving peel resistance, and can greatly extend the life. .
【００２２】基材のサイズ、形状、厚みなどは、特に制
限されず、目的又は用途に応じて、適当に選択できる。The size, shape, thickness and the like of the substrate are not particularly limited, and can be appropriately selected according to the purpose or application.
【００２３】［耐熱部材］本発明の耐熱部材には、前記
耐熱合金製基材の表面に、前記第１のコーティング材で
構成された耐熱層が形成されている。[Heat-Resistant Member] In the heat-resistant member of the present invention, a heat-resistant layer composed of the first coating material is formed on the surface of the heat-resistant alloy base material.
【００２４】前記耐熱層の厚みは、基材に耐熱性を付与
できる限り、特に制限されず、例えば、１０〜１０００
μｍ、好ましくは５０〜５００μｍ、さらに好ましくは
１００〜３００μｍ程度である。The thickness of the heat-resistant layer is not particularly limited as long as heat resistance can be imparted to the substrate.
μm, preferably about 50 to 500 μm, and more preferably about 100 to 300 μm.
【００２５】図１は、本発明の一例を示す断面図であ
る。この例においては、基材３上に形成された耐熱層
（中間層）２の表面には、さらに、遮熱性を有する表面
層１が形成されている。このように、第１のコーティン
グ材と第２のコーティング材とを組み合わせてコーティ
ングシステムとしても有利に利用できる。前記中間層
は、前記第１のコーティング材で形成されているため、
ＺｒＯ2系セラミックスで構成された第２のコーティン
グ材で表面層を形成すると、耐熱層と表面層との密着性
を向上させることができる。FIG. 1 is a sectional view showing an example of the present invention. In this example, on the surface of the heat-resistant layer (intermediate layer) 2 formed on the base material 3, a surface layer 1 having heat-shielding properties is further formed. Thus, the first coating material and the second coating material can be advantageously used as a coating system in combination. Since the intermediate layer is formed of the first coating material,
When the surface layer is formed of the second coating material made of ZrO 2 -based ceramic, the adhesion between the heat-resistant layer and the surface layer can be improved.
【００２６】ＺｒＯ2（ジルコニア）系セラミックス
は、相転移による体積変化が大きいため、通常、ＺｒＯ
2セラミックスを安定剤により安定化して使用する。こ
のような安定剤としては、ジルコニアに固溶可能な酸化
物、例えば、Ｙ2Ｏ3、ＭｇＯ、ＣｅＯ2、ＣａＯなどが
挙げられる。安定剤は、一種で又は二種以上組み合わせ
て使用できる。ZrO 2 (zirconia) -based ceramics have a large volume change due to a phase transition, and are usually ZrO 2 (zirconia) -based ceramics.
2 Use ceramics stabilized with a stabilizer. Examples of such a stabilizer include oxides that can be dissolved in zirconia, such as Y 2 O 3 , MgO, CeO 2 , and CaO. The stabilizers can be used alone or in combination of two or more.
【００２７】ジルコニア系セラミックスは、比較的低含
量の安定剤で安定化された部分安定化ジルコニア系セラ
ミックスであるのが好ましい。部分安定化ジルコニア系
セラミックスにおいて、安定剤の含量は、ジルコニア系
セラミックスに対して、０．１〜２５重量％、好ましく
は１〜２０重量％、さらに好ましくは５〜１５重量％程
度である。The zirconia ceramic is preferably a partially stabilized zirconia ceramic stabilized with a relatively low content of a stabilizer. In the partially stabilized zirconia-based ceramic, the content of the stabilizer is about 0.1 to 25% by weight, preferably about 1 to 20% by weight, and more preferably about 5 to 15% by weight, based on the zirconia-based ceramic.
【００２８】セラミックスの相構造（表面及び界面構
造；粒及び空孔の大きさ、分布などの微構造など）は、
特に制限されない。また、表面層の厚みは、特に制限さ
れず、前記耐熱層の厚みと同程度の厚みから選択でき
る。表面層の厚みと耐熱層の厚みとの割合は、前者／後
者＝１／５〜５／１、好ましくは１／２〜２／１、さら
に好ましくは４／５〜６／５程度である。The phase structure of ceramics (surface and interface structure; microstructure such as size and distribution of grains and pores, etc.)
There is no particular limitation. The thickness of the surface layer is not particularly limited, and can be selected from the same thickness as the thickness of the heat-resistant layer. The ratio of the thickness of the surface layer to the thickness of the heat-resistant layer is the former / the latter = 1/5 to 5/1, preferably 1/2 to 2/1, and more preferably about 4/5 to 6/5.
【００２９】このような耐熱部材は、基材に、第１のコ
ーティング材の皮膜（耐熱層）、必要により第２のコー
ティング材の皮膜（表面層）を形成することにより製造
できる。Such a heat-resistant member can be manufactured by forming a film (heat-resistant layer) of the first coating material and, if necessary, a film (surface layer) of the second coating material on the substrate.
【００３０】耐熱層は、慣用のコーティング方法、例え
ば、溶射法（プラズマ溶射、レーザー溶射、減圧プラズ
マ・レーザー複合溶射などの電気式溶射など）により形
成できる。プラズマ溶射には、大気プラズマ溶射法、水
プラズマ溶射法、減圧プラズマ溶射法、高周波誘導プラ
ズマ溶射などが含まれ、特に減圧プラズマ溶射法が好ま
しい。The heat-resistant layer can be formed by a conventional coating method, for example, a thermal spraying method (electric spraying such as plasma spraying, laser spraying, and reduced pressure plasma / laser combined spraying). The plasma spraying includes an atmospheric plasma spraying method, a water plasma spraying method, a reduced pressure plasma spraying method, a high frequency induction plasma spraying, and the like, and a reduced pressure plasma spraying method is particularly preferable.
【００３１】表面層は、慣用のセラミックス膜形成方
法、例えば、上記大気プラズマ溶射法などの溶射被覆法
などにより形成できる。The surface layer can be formed by a conventional method of forming a ceramic film, for example, a spray coating method such as the above-mentioned atmospheric plasma spray method.
【００３２】本発明は、高度の耐熱性能が要求される用
途、例えば、ガスタービン用翼（産業又は工業用ガスタ
ービン用動翼及び静翼など）の他、ジェットエンジン用
翼（動翼及び静翼）などの用途に有用である。The present invention is applicable to applications requiring high heat resistance, such as blades for gas turbines (such as moving blades and stationary blades for industrial or industrial gas turbines), as well as blades for jet engines (moving blades and stationary blades). It is useful for applications such as wings.
【００３３】[0033]
【発明の効果】本発明では、Ｎｉ及びＣｏを併用するＭ
ＣｒＡｌＹ成分において、特定のＣｒ、Ａｌ及びＹ含量
を有する成分を用いて、第１のコーティング材を構成す
るので、低コストでありながらも、コーティング材及び
耐熱部材の耐熱性及び耐久性を大幅に改善できる。ま
た、前記第１のコーティング材で構成された耐熱層を、
第２のコーティング材でさらにコーティングすることに
より、コーティングシステム全体として、剥離寿命を大
幅に延長できる。According to the present invention, M is used in combination with Ni and Co.
In the CrAlY component, the first coating material is constituted by using a component having specific Cr, Al and Y contents, so that the heat resistance and the durability of the coating material and the heat-resistant member are significantly reduced while being low in cost. Can be improved. In addition, the heat-resistant layer composed of the first coating material,
By further coating with the second coating material, the peel life of the coating system as a whole can be greatly extended.
【００３４】[0034]
【実施例】以下に、実施例に基づいて本発明をより詳細
に説明するが、本発明はこれらの実施例によって限定さ
れるものではない。The present invention will be described below in more detail with reference to Examples, but the present invention is not limited to these Examples.
【００３５】実施例１〜３ （サンプルの作製）Ｃｏ基鋳造合金（Ｍａｒ−Ｍ５０
９）を用いて、板状試験片（縦５０ｍｍ，横６０ｍｍ，
厚み３ｍｍ）］を作製し、基材とした。前記Ｍａｒ−Ｍ
５０９の主な含有成分の割合を表１に示す。Examples 1 to 3 (Preparation of Sample) Co-base casting alloy (Mar-M50)
9), a plate-like test piece (50 mm long, 60 mm wide,
Thickness 3 mm)] was prepared and used as a substrate. Mar-M
Table 1 shows the proportions of the main components 509.
【００３６】[0036]
【表１】 [Table 1]
【００３７】表２に示す割合の成分を含有するＭＣｒＡ
ｌＹを作製し、下記の条件で、前記基材上に減圧プラズ
マ溶射し、膜厚１９０〜２１０μｍの耐熱層を形成し
た。MCrA containing the components shown in Table 2
1Y was prepared and subjected to reduced pressure plasma spraying on the substrate under the following conditions to form a heat-resistant layer having a thickness of 190 to 210 μm.
【００３８】 前記耐熱層上に、下記の条件で、Ｙ2Ｏ3安定化ＺｒＯ2
（Ｋ−９０，昭和電工（株）製，主な成分の割合：Ｚｒ
Ｏ2 ９０．６１重量％，Ｙ2Ｏ3 ８．５２重量％，Ａ
ｌ2Ｏ3 ０．０２重量％，ＳｉＯ2 ０．１１重量％，
Ｆｅ2Ｏ3 ０．０８重量％）を大気プラズマ溶射し、膜
厚１９０〜２１０μｍの表面層を形成した。[0038] On the heat-resistant layer, under the following conditions, Y 2 O 3 -stabilized ZrO 2
(K-90, manufactured by Showa Denko KK, ratio of main components: Zr
90.61% by weight of O 2, 8.52% by weight of Y 2 O 3 ,
l 2 O 3 0.02% by weight, SiO 2 0.11% by weight,
The Fe 2 O 3 0.08 wt%) and air plasma spraying, to form a surface layer having a thickness 190～210Myuemu.
【００３９】 （耐熱性（耐久性）の評価）実施例で得られた各サンプ
ルを、強制冷却型高温熱サイクル炉を用い、最高温度１
１５０℃とする下記熱サイクル負荷試験に供し、コーテ
ィングの剥離が発生するまでのサイクル数をカウントし
た。なお、熱負荷の形態として、(1)１５分かけて３０
０℃から１１５０℃まで連続的に昇温し、次いで(2)４
０分間１１５０℃に維持し、その後(3)５０分かけて１
１５０℃から３００℃まで連続的に降温（冷却）する３
ステップで構成された熱サイクル負荷試験を１サイクル
とした。[0039] (Evaluation of heat resistance (durability)) Each sample obtained in the example was subjected to a maximum temperature of 1 using a forced cooling type high temperature heat cycle furnace.
The sample was subjected to the following thermal cycle load test at 150 ° C., and the number of cycles until the peeling of the coating occurred was counted. In addition, as a form of the heat load, (1) 30 minutes over 15 minutes
The temperature is continuously raised from 0 ° C to 1150 ° C, then (2) 4
Maintain the temperature at 1150 ° C for 0 minutes, and then (3) 1 minute over 50 minutes.
Continuous cooling (cooling) from 150 ° C to 300 ° C 3
The heat cycle load test composed of steps was one cycle.
【００４０】比較例１ 耐熱層として、表２に示す割合の成分を含有するＭＣｒ
ＡｌＹ（ＡＭＤＲＹ９９５１，スルザーメテコジャパン
（株）製）を用いる以外は、実施例と同様に基材、耐熱
層及び表面層を形成し、耐熱性を評価した。Comparative Example 1 As a heat-resistant layer, MCr containing the components shown in Table 2 was used.
A substrate, a heat-resistant layer, and a surface layer were formed in the same manner as in Example, except that AlY (AMRY9951, manufactured by Sulzer Metco Japan KK) was used, and heat resistance was evaluated.
【００４１】比較例２ 耐熱層として、表２に示す割合の成分を含有するＭＣｒ
ＡｌＹを用いる以外は、実施例と同様に、基材、耐熱層
及び表面層を形成し、耐熱性を評価した。Comparative Example 2 As a heat-resistant layer, MCr containing components in the proportions shown in Table 2
Except for using AlY, a substrate, a heat-resistant layer and a surface layer were formed in the same manner as in the example, and the heat resistance was evaluated.
【００４２】実施例及び比較例で用いた耐熱層の主な成
分の割合と共に、各サンプルの破断サイクル数を表２に
示す。Table 2 shows the number of break cycles of each sample together with the ratio of the main components of the heat-resistant layer used in Examples and Comparative Examples.
【００４３】[0043]
【表２】 [Table 2]
【００４４】表２より明らかなように、実施例では、耐
久性が、比較例に比べて大幅に向上している。特に実施
例１では、耐熱層を市販品で形成した比較例１に比べて
二倍近くも剥離寿命が延長されている。As is clear from Table 2, the durability of the example is greatly improved as compared with the comparative example. In particular, in Example 1, the peeling life was extended by almost twice as compared with Comparative Example 1 in which the heat-resistant layer was formed of a commercial product.
【図１】図１は、本発明の耐熱部材の一例を示す断面図
である。FIG. 1 is a sectional view showing an example of a heat-resistant member of the present invention.
１…表面層 ２…耐熱層 ３…基材 1: Surface layer 2: Heat resistant layer 3: Base material
フロントページの続き Ｆターム(参考） 4J038 AA011 HA066 HA196 HA216 KA09 NA03 NA14 PA06 PB07 PB09 PC02 4K031 AA02 AB03 AB06 AB08 CB11 CB14 CB21 CB22 CB27 CB42 DA04 DA07 EA10 Continued on the front page F term (reference) 4J038 AA011 HA066 HA196 HA216 KA09 NA03 NA14 PA06 PB07 PB09 PC02 4K031 AA02 AB03 AB06 AB08 CB11 CB14 CB21 CB22 CB27 CB42 DA04 DA07 EA10
Claims (8)
のコーティング材であって、下記式 ＭＣｒＡｌＹ （式中、ＭはＮｉ及びＣｏを示す）で表される成分と不
可避的不純物とで構成され、Ｃｒ含量が２１〜２８重量
％、Ａｌ含量が４〜７．５重量％、及びＹ含量が０．０
５〜１．２重量％であるコーティング材。1. A coating material for coating a substrate made of a heat-resistant alloy, comprising a component represented by the following formula MCrAlY (where M represents Ni and Co) and unavoidable impurities, Cr content of 21 to 28% by weight, Al content of 4 to 7.5% by weight, and Y content of 0.0
A coating material that is 5 to 1.2% by weight.
部に対するＡｌの割合が６〜１０重量部である請求項１
記載のコーティング材。2. The method according to claim 1, wherein the proportion of Al is 6 to 10 parts by weight based on 100 parts by weight of the total amount of nickel and cobalt.
The coating material as described.
求項１記載のコーティング材。3. The coating material according to claim 1, wherein the Y content is 0.8 to 1.2% by weight.
量％のＡｌ及び１〜１．２重量％のＹと、不可避的不純
物と、残余のＮｉ及びＣｏとで構成され、ＮｉとＣｏと
の重量割合がＮｉ／Ｃｏ＝１０／９０〜９０／１０であ
る請求項１記載のコーティング材。4. An alloy comprising 23 to 26% by weight of Cr, 5 to 6.5% by weight of Al and 1 to 1.2% by weight of Y, unavoidable impurities, and the balance of Ni and Co. 2. The coating material according to claim 1, wherein the weight ratio between Co and Co is Ni / Co = 10/90 to 90/10. 3.
れた耐熱層上に表面層を形成するためのコーティング材
であって、Ｙ2Ｏ3、ＭｇＯ、ＣｅＯ2及びＣａＯから選
択された少なくとも一種の安定剤０．１〜２５重量％で
安定化されたＺｒＯ2系セラミックスで構成されている
コーティング材。5. A coating material for forming a surface layer on the heat-resistant layer composed of the coating material according to claim 1, wherein at least one selected from Y 2 O 3 , MgO, CeO 2 and CaO. A coating material comprising a ZrO 2 -based ceramic stabilized with 0.1 to 25% by weight of the stabilizer.
のコーティング材で構成された耐熱層が形成されている
耐熱部材。6. A heat-resistant member having a heat-resistant layer made of the coating material according to claim 1 formed on a surface of a heat-resistant alloy base material.
成された基材の表面に耐熱層が形成され、さらにこの耐
熱層の表面に請求項５記載のＺｒＯ2系セラミックスで
構成された表面層が形成されている請求項６記載の耐熱
部材。7. A heat-resistant layer formed on the surface of a base material made of a heat-resistant alloy having a Co content of 45% by weight or more, and a surface made of the ZrO 2 -based ceramic according to claim 5 on the surface of this heat-resistant layer. The heat-resistant member according to claim 6, wherein a layer is formed.
耐熱部材。8. The heat-resistant member according to claim 6, which is a gas turbine blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000184789A JP2002003747A (en) | 2000-06-20 | 2000-06-20 | Coating material and heat-resistant member using the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000184789A JP2002003747A (en) | 2000-06-20 | 2000-06-20 | Coating material and heat-resistant member using the same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2002003747A true JP2002003747A (en) | 2002-01-09 |
Family
ID=18685193
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2000184789A Pending JP2002003747A (en) | 2000-06-20 | 2000-06-20 | Coating material and heat-resistant member using the same |
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| Country | Link |
|---|---|
| JP (1) | JP2002003747A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005097727A (en) * | 2003-08-07 | 2005-04-14 | Snecma Moteurs | Thermal barrier composition, superalloy mechanical part coated with the thermal barrier composition, ceramic coating, and method of making the coating |
| JP2009133240A (en) * | 2007-11-29 | 2009-06-18 | Mitsubishi Heavy Ind Ltd | Thermal barrier coating, gas turbine component and gas turbine using the same |
| WO2010070982A1 (en) | 2008-12-16 | 2010-06-24 | 旭硝子株式会社 | Filmed metal member for float glass manufacturing equipment and float glass manufacturing method |
| DE102012101105B4 (en) | 2011-02-10 | 2019-09-05 | Ngk Spark Plug Co., Ltd. | spark plug |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55161041A (en) * | 1979-05-29 | 1980-12-15 | Howmet Turbine Components | Covering material |
| JPS58141355A (en) * | 1982-02-18 | 1983-08-22 | Hitachi Metals Ltd | Alloy having coating layer |
-
2000
- 2000-06-20 JP JP2000184789A patent/JP2002003747A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55161041A (en) * | 1979-05-29 | 1980-12-15 | Howmet Turbine Components | Covering material |
| JPS58141355A (en) * | 1982-02-18 | 1983-08-22 | Hitachi Metals Ltd | Alloy having coating layer |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005097727A (en) * | 2003-08-07 | 2005-04-14 | Snecma Moteurs | Thermal barrier composition, superalloy mechanical part coated with the thermal barrier composition, ceramic coating, and method of making the coating |
| JP4538276B2 (en) * | 2003-08-07 | 2010-09-08 | スネクマ | Thermal barrier composition, superalloy mechanical part with coating having such composition, ceramic coating, and method of making the coating |
| JP2009133240A (en) * | 2007-11-29 | 2009-06-18 | Mitsubishi Heavy Ind Ltd | Thermal barrier coating, gas turbine component and gas turbine using the same |
| WO2010070982A1 (en) | 2008-12-16 | 2010-06-24 | 旭硝子株式会社 | Filmed metal member for float glass manufacturing equipment and float glass manufacturing method |
| KR20110111378A (en) | 2008-12-16 | 2011-10-11 | 아사히 가라스 가부시키가이샤 | Filmed metal member for float glass manufacturing equipment and float glass manufacturing method |
| DE102012101105B4 (en) | 2011-02-10 | 2019-09-05 | Ngk Spark Plug Co., Ltd. | spark plug |
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